Combined radial and axial flow multistage turbine



April 8, 1952 c. YEOMANS 2,592,227

COMBINED RADIAL AND AXIAL FLOW MULTISTAGE TURBINE Filed Oct. 24, 1944 6 Sheets-Sheet 1 B, @Mm

April 8,1952 c. YYYYY NS 2,592,227

(L //-r0/v YEOMANS,

Attorneys C. YEOMANS April 8, 1952 COMBINED RADIAL AND AXIAL FLOW MULTIS'IAGE TURBINE 6 Sheets-Sheet 5 Filed Oct. 24, 1944 Inventor Attoeys April 8, 1952 c. YEOMANS 2,592,227

COMBINED RADIAL AND AXIAL FLOW MULTISTAGEI TURBINE Filed Oct. 24, 1944 6 Sheets-Sheet 4 u v H f 9 /O? k? l2 Inventor CL IFTON YEOMA N5,

Attorneys c. YEOMANS 2,592,227

COMBINED RADIAL AND AXIAL FLOW MULTISTAGE TURBINE April 8, 1952 6 Sheets-Sheet 5 Filed Oct. 24, 1944 CL/FTON )Z-OMAMS,

and

April 8, 1952 c. YEOMANS 2,592,227

- COMBINED RADIAL AND AXIAL. FLOW MULTISTAGE TURBINE Filed Oct. 24, 1944 6 Sheets-Sheet 6 G G Inventor CLIFTON YEOMA N5,

Patented Apr. 8, 1952 OFFICE COMBINED RADIAL AND AXIAL FLOW MULTISTAGE TURBINE Clifton Yeomans, Washington, D. C.

Application October 24, 1944, Serial No. 560,124

Claims.

This invention relates to turbines and although it has specific reference to turbines operated by a gaseous fluid or by a gaseous fluid mixed with steam; it also has reference to turbines driven solely by steam.

The primary object of the invention consists in a turbine in which the thermal and pressure energy of the driving fluid is converted into mechanical power within a minimum of space and with a minimum of weight of the parts necessary to produce the desired conversion.

Another object of the invention consists in providing a turbine which may be operated either as an internal combustion engine, utilizing the gases due to the explosion of a mixture of a fuel and air or may be operated with a mixture of steam and combustion gases or may be operated by steam alone acting as a driving fluid.

A further object of the invention consists in an action and reaction turbine in which the energy of the driving fluid is transformed into mechanical power by a tangential and axial flow of the fluid.

A further object of the invention consists in an action and reaction turbine in which the energy of the driving fluid is transformed into mechanical power by a tangential and axial flow of the fluid.

A further object of the invention consists in providing a turbine of the internal combustion type supplying itself with the air for combustion and being simultaneously equipped for the production of steam within the power unit.

A further object of the invention consists in utilizing'the space surrounding the axis of the rotor for the purpose of generating steam.

A still further object of the invention consists in providing a combined turbine and compressor unit, occupying a minimum of space and producing the compression of air necessary for combustion before it enters the combustion chamber.

A number of other objects and advantages will be apparent to those skilled in theart or will be specially referred to in the following detailed specification describing several modifications of the invention. This description by referring to the drawings showing these modifications has to describe specific examples of constructions but it is to be understood that the invention consists in the arrangement, construction and combination of parts in general as outlined in the annexed claims and that the specific examples are described by way of illustrating the best mode of carrying the invention into effect, but are not the exhaust side;

Figure 3 is a cross section through the turbine along line 3-3 in Figure 5, part of this section being broken away, this part showing another cross section along line 3a3a of Figure 5. The cross section along line 3-3 runs through the admission side, the cross section along line 3a7-3a through the exhaust side of one stage of the rotor;

Figure 4 is a plan view of the turbine with the upper casing removed showing the lower casing, the jet opening cylinder, partly broken away, and the rotor with its blades;

Figure 5 is an elevational longitudinal section through the turbine according to the invention;

Figure 6 is an elevational longitudinal section through a modification of the invention in which the turbine is combined with an air compressor, and in which the jets acting in the rotor in the various stages are produced by means of a number of rings, equal to the number of stages, each ring being provided with guiding blades;

Figures 7 and 8 are views of small strips of the compressor rotor with the casing removed showing the blades of the compressor;

Figure ,9 is an end view of the same modifica tion, partly in section along the line 9-9 of Figure 6;

Figures 10, 11, and 12 are parts of sectional views, showing cross sections through the compressor and rotor along the lines Ill-I0; Il-l I;

l2-l 2; of Figure 6, respectively.

Figure 13 is another sectional view showing a cross section through the compressor and rotor along line I 3l3 of Figure 6, which illustrates in detail the ring construction and shows the blades arranged on the rings.

As seen in Figures 1 through 5, th improved turbine comprises a casing 20, enclosing a rotor 2| mounted on a shaft 22.

The casing 20, as shown in Figures 1 and 2 consists of two parts joined by flanges 23, 24. It is supported by a supporting flange 25 which rests on the structure carrying the installation.

The interior of the turbine may be divided into sections or chambers. Near the front or entrance in any way limitative and that other specific end is the air chamber 26, towhich air is admitted through the openings 21 (Figure 1) when the turbine is operated as an internal combustion engine with or without admixture of steam to the gases produced by explosion. This air is blown into the combustion chamber 28 by means of ventilator blades 29 arranged at the front end of the rotor 2| on the wall 30 which closes the said front end.

Into the combustion chamber 28 pipes 3| (Figures 1 and 5) are projecting through which the liquid fuel, such as gasoline, alcohol, or heavy fuel oils, is admitted. This chamber also carries a number of spark plugs 32, which are operated at predetermined intervals by an igniting device (not shown), and are mainly used in the starting phase, when the interior of the combustion chamber still has a low temperature.

Thesecond section 34 is the expansion or rotor chamber, which houses the rotor 2|. consists of a body which is cylindrical at the outside and conical at the inside; the periphery is provided with a number of channels or grooves of semi-toroidal form 35, 36, 31, 38 with gradually enlarged cross sections within which the blades are arranged. The blades 39 are appropriately spaced within these channelsand are inclined with respect to the axis of the cylindrical surface and of the turbine as clearly seen in Figure 4.

This inclination may also be defined as an in-- clination of the edge of the blade, located in or near the cylindrical. circumference, towards an element or a generatrix of the cylindrical surface, passing through one point of said edge. By virtue of this inclination an action of the gas (or steam) jet on the rotor is exercised as the impact of the jet on the blades produces forces having a component acting in a plane perpendicular to the axis of the turbine and thereby produces rotation around said axis.

This inclination of the blades 39, 39a, 39b, 390 as seen when comparing Figure 3 with Figure 5 is such that the blades are not only inclined at an angle to the axis of the rotor as above defined but are also inclined with respect to the periphery of the rotor, so that they are tangents to an ideal cylinder (or cone) around the axis in addition to being inclined with respect to the latter. As the blades are inclined in two directions it will be easily understood that in addition to the action exercised by the jet and producin a rotary movement by virtue of a component acting in a plane perpendicular to the axis, the change of direction of the fluid streaming along the blades within the toroidal channel or groove of the rotor will also produce a component in the plane, so that the rotor is driven both by action due to the jet and by reaction due to change of direction.

As already described the rotor is provided with a plurality of semi-toroidal channels or grooves 35, 36, 31, 38 carrying blades 39 and each channel represents a stage of expansion. The channels or grooves 35, 36, 31, 38 are, therefore, of unequal width and depth, which are increasing'towards the exit or exhaust end.

The rotor 2| is keyed to the shaft 22 and surrounds a central hollow space or chamber 40, which is closed on the ends by walls 30 and 4|, which at the same time serve to support the rotor 2| on the shaft 22. This central space is tightly sealed (by means not shown) and forms the steam generating chamber of the turbine in those cases in which steam is to be admittedto the expanding combustion gases.

The generation of steam is obtained by admit- The latter 4 ting water to said chamber which, as will be clear, is brought to a very high temperature.

Water is admitted through a channel 43 in shaft 22 on which the rotor 2| is mounted. This shaft is journaled in bearings 44, 45 connected with the casing 20 by means of connecting shields 46. The said bearings are supported on the structure supporting the entire installation.

Forintroducing the water a separate water admission collar 41 is provided. It surrounds the shaft 22 like a bearing and is provided with a cavity 48 to which water under pressure is admitted by means of pipes 49. The shaft 22 is provided with a groove 58 into which several radial channels 5| open which all communicate with a central channel 52. The latter again communicates with the outwardly inclined channel 43.

The water is forced into the chamber 40 and is converted into steam under pressure on account of the high temperature of the rotor. The steam penetrates into the grooves 35 by means of the openings 55 into which short pipe sections 56 are inserted. These pipe sections are of such lengths that they prevent the admission of water which may have collected on the bottom of the rotor especially during the starting stage.

The next section of the turbine is the reaction chamber 58 which comprises the part of the casing surrounding the rotor 2|. This section is adjacent to the combustion chamber 28 and comprises a number of semi-toroidal grooves or channels 59, 66, 6| whose size increases gradually in the same way in which the grooves in the rotor are increasing. Between these grooves there are ledges 62, 63, 64, 65, and these ledges serve to support the jet-opening and discharge-openingcylinder 10 which is provided along its periphery with jet or admission openings 12, 13, 14 for every expansion stage and rotor channel 35, 36, 31, 38. Similarly, this cylinder is provided with dischargebr exhaust openings 80, 8|, 82 through which the gases mixed with steam are discharged in every stage. The toroidal channels 59, 60, 6|, 62 are not provided with blades and admission is simply regulated by the jetand dischargeopening cylinder.

It will be clear from Figures 4 and 5 that the gases from the combustion chamber 28 will pass through openings 1|, pass channel 35 of the rotor, entering between blades 39, pass through discharge openings of cylinder 13, reenter openings 12 of cylinder 10, pass between the blades of rotor channel 36 and continue to pass through the channels of the casing which reverse the direction and through the channels of the rotor until they reach the exhaust chamber 15. From there they are carried away through the exhaust openings 16 (Figure 2) to an exhaust pipe- (not shown).

It will be noted from Figure 3 that the openings II are not radially directed but are inclined, preferably at an angle which is larger than the angle at which the blades are inclined in this projection in order to reduce resistance during transition from the stationary totliemoving part. Similarly, the discharge openings 8|].are inclined at an angle less than the angle of the blades, this reduction resulting mostly in an apparent inclination in the other direction to reduce resistance during the passage from. the moving to the stationary part.

The operation of the turbine is possible with steam alone, or with expansion gases mixed with steam. The lattter is added to the gases for cooling the rotor and for reducing the temperature at which the parts operate in order to reduce the corrosion of the parts of the turbine.

When operating with steam, the latter is admitted under appropriate pressure through the openings 21 and the blades or vanes 29 may be omitted. No steam is then admitted into the interior of the turbine rotor. I

Figures 6 to 13 show another modification of the turbine which is designed for explosive gases which have to be mixed with air.

In this modification the shaft 22 and the rotor 2| are substantially identical with the corresponding parts of the modification as above described. They need not be described in detail. The casing, however, is of a different construction. Y As seen in Figure 6, the casing is provided with an outer section 90 housing an air compressor and with an inner section 9| housing the rotor. The inner section 9I in this modication is conical and has a smooth inner surface. The channels of the reaction section of the casing are formed by separate rings 93, 94, 95, 96 which are fixedly mounted within said conical surface and may be held firmly by appropriate means such as screws (not shown) and by caulking after having been fitted properly. The said rings 93, 94, 95, 96 may be provided with blades 91, as clearly seen in Figure 13, sub-dividing the gas stream and producing the desired jet effect. The cylindrical sleeve inserted between the casing and the rotor, such as shown in the modification illustrated in Figure 4, can therefore be dispensed with. The rings may be relatively short with an arcuate inner surface covering an arc of only 90.

On the outside the conical part 9I of the casing presents a stepped appearance. It forms the inner surface of a multi-stage rotary compressor which provides the combustion chamber 28 with compressed air.

The said multi-stage compressor is enclosed in v a casing 90 of conical shape which may be stepped on the inside. This outer casing 90 is fixed to the turbine casing by means of a large number of radial ribs or spokes 98 (Figure 9) holding a ring 99 which is V-shaped and surrounds the combustion chamber 28; said ring is closed by the front wall I 0 I.

The rear part of the outer casing 90 is joined to the inner casing 92 and to the rear wall I02 of the casing by a ring I03.

In the space between the two members 99 and 9| the rotor of the compressor is inserted which comprises a conical blade carrier I00 fixed to the front wall 30 of the rotor 2| by a number of ribs I04 between which the gases may enter from the combustion chamber into the rotor. The ribs I 04 carry a ring I95 which forms a projecting dish-like collar guiding the compressed air which is discharged by the compressor into the combustion chamber.

The blade carrier I00 carries two series of blades I06 and I0! one at the inside and one at the outside. The outer set I06 diminishes in size from the front end to the rear end of the casing in accordance with the increasing pressure while the second set I01 decreases in size from the rear side to the front side. A plan view of a strip of the blade carrier I09 with blades I06 arranged at the outside of the carrier is shown in Figure 7, while a similar strip showing the blades on the inside is shown in Figure 8. The blades have any well-known ,6 shape and are arranged in rows around the blade carrier I00.

The air is drawn in between the ribs 99 and is driven by blades I06 towards the rear end of the casing being more and more compressed during this flow. When the air reaches the chamber I08 on the rear of the casing, which may be provided with radial ribs I09, its direction of flow is reversed (as shown by the arrow) and it is now driven by blades I01 towards the front end, being compressed on the way. It finally is discharged over the collar I05 into the combustion chamber; it has acquired a high pressure during the process and it may therefore be used in connection with heavy fuel oils which are injected through pipes 3|.

In other respects, the turbine will operate like the modification shown in Figures 1 to 5.

It will be seen from the above that the turbine according to the invention is an action-reaction turbine combining the advantages of the tangential fiow turbine with those of the axial flow turbine. It will also be seen that the turbine may have any size; it may merely have the size of a motor driving a tool or the like, a feature which isof great advantage. The construction is moreover such that a minimum of distortion under the high temperatures will occur V "The jet effect produced in each stage allows a certain amount of clearance and a certain amount of distortion may even take place without binding between the moving and the stationary parts.

It will moreover be noted that all the parts used may be easily/machined with great precision.

The examples described show a definite direction of rotation, which may be reversed, as well known, by reversing the position of the blades and jet openings with respect to the shaft.

I claim:

1. A multistage turbine for operation with elastic fluids passing through the turbine in a combined axial and radial flow, comprising a rotor with a cylindrical outer surface, provided witha series of juxtaposed radially extending circumferential grooves of substantially semicircular cross section of increasing width and depth in the direction of axial flow, blades arranged within said grooves inclined tangentially and axially, so that a line proceeding along the blade towards the axis of the cylindrical surface is inclined with respect to a radial plane passing through said axis and a line running along the blade in an axial direction is inclined with respect to the elements of the cylinder, a stator with a cylindrical inner surface provided with a series of juxtaposed radially extending circumferential grooves of substantially semi-circular cross section, of a width and depth increasing in the direction of flow, acting as flow direction reversing chambers, the grooves in the rotor and stator being staggered and a flow dividing cylinder, arranged between the cylindrical surfaces of the rotor and the stator, provided with inlet and outlet openings, the former subdividing the circumferential continuous radial flow of the fluid emerging from the flow reversing circumferential grooves of the stator into a number of separate jets.

2. A multistage turbine for operation with elastic fluids passing through the turbine in a combined axial and radial flow, comprising a rotor with a cylindrical outer surface, provided with a series of juxtaposed radially extending circumferential grooves of substantially semicircular.- cross section of increasing width and depth in the direction of axial flow, blades arranged within said grooves inclined tangentially and axially, so that a. line proceeding along the blade towards the axis of the cylindrical surface is inclined with respect to a radial plane passing through said axis and a line running along the blade in an axial, direction is inclined with respcct .to the elements of the cylinder, a stator with. a cylindrical inner surface provided with a series of juxtaposed radially extending circumferentialgrooves of substantially semi-circular cross section, of a width and depth increasing in the direction of flow, acting as flow direction reversing chambers, the grooves in the rotor and stator being staggered and a flow dividing cylinder arranged between the cylindrical surfaces of the stator and; the rotor, provided with inlet and outlet openings of an increased axial Width, arranged so as to coincide with stator and rotor grooves respectively, the width of each opening not exceeding one-half of the axial width of the stator and rotor groove covered by the said ope ng.

3; A multistage turbine for operation with elastic fluids passing through the turbine in a combinedaxial and radial flow, comprising a rotor with a, cylindrical outer surface, provided with a series .of juxtaposed radially extending circumferential grooves of substantially semi-circular cross ,section, of increasing width and depth in thedirection of axial flow, blades arranged within said grooves inclined tangentially and axially, so that a line proceeding along the blade-towards' the axis of the cylindrical surface is inclined with respect to a radial plane passing through said axis and a line running along the blade in an axial direction is inclined with respect to the elements of the cylinder, a stator with a cylindrical inner surface provided with a series of juxtaposed radially extending circumferential grooves of substantially semi-circular cross section, of a width and depth increasing in the direction of flow, acting as flow direction reversing chambers, the grooves in the rotor and stator being staggered and a flow dividing cylindrical member interposed between the cylindrical surfaces of the stator and rotor, said member being subdivided into separate axially spaced circumferential zones of increasing axial width, a continuous series of ports being provided in said member along said zones, and said member being arranged between the stator and the rotor so that the zones coincide with the overlapping portions of the-staggered circumferential grooves in the stator and the rotor, adjacent zones being provided with inlet and outlet openings respectively, the numberof the former being equal to the number of'blades in the adjacent circumferential rotor groove, so as to subdivide the fluid emerging from a flow reversing stator groove into a number of jets equal to the number of blades in the rotor groove.

4. VA multistage turbine for operation with elastic fluids as'claimed in claim 1 wherein the inlet openings are provided with radially inclined walls which are also inclined at an angle to. the adjacent portionof the blade.

5. .The combination of claim 1 including means for generating and'introducing steam into the first stage of the turbine.

CLIFTON YEOMANS.

REFERENCES CITED The following references are of recordin the file of this patent:

UNITED STATES PATENTS Number Name Date 635,919 Curtis Oct. 31, 1899 762,449 Sturgeon June 14, 1904 860,573 Sayers July 16, 1907 1,003,203 Rearick Sept. 12, 1911 1,077,300 Rearick Nov. 4, 1913 1,139,696 Maxwell May 18, 1915 1,164,091 Herz Dec. 14, 1915 1,315,230 Mallory Sept. 9, 1919 1,418,444 Josephs June 6,1922 1,421,087 Johnson June 27, 1922 1,442,876 Hartman Jan. 23, 1923 1,676,806 Smalley July 10, 1928 1,828,782 Morton Oct. 27, 1931 1,864,742 Koch June 28, 1932 FOREIGN PATENTS Number Country Date 23,713 Great Britain NOV. 2, 1903 

